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Overall engine efficiency rating for turbomachine engines

Active Publication Date: 2022-10-11
GE AVIO +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The patent text describes a method for rating the efficiency of a turbomachine engine by measuring the flow rate of oil, the diameter of the fan blades, and the net thrust of the engine. This rating can help optimize the engine's components and improve its overall architecture. It can also aid in the development of the fan, gearbox, and low-pressure turbine. By using this rating, the method provides more efficient turbomachine engines and simplifies the development process.

Problems solved by technology

For example, including a gearbox in a turbofan engine introduces additional complexity to the engine.
This can, for example, make engine development and / or manufacturing significantly more difficult.

Method used

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  • Overall engine efficiency rating for turbomachine engines
  • Overall engine efficiency rating for turbomachine engines
  • Overall engine efficiency rating for turbomachine engines

Examples

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Embodiment Construction

[0055]Reference now will be made in detail to examples of the disclosed technology, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the disclosed technology, not a limitation of the disclosure. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present disclosure without departing from the scope or spirit of the disclosure. For instance, features illustrated or described as part of one example can be used with another example to yield a still further example. Thus, it is intended that the present disclosure covers such modifications and variations as come within the scope of the appended claims and their equivalents.

[0056]The word “exemplary” is used herein to mean “serving as an example, instance, or illustration.” Any implementation described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other implementatio...

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Abstract

A turbomachine engine can include a fan assembly, a vane assembly, a core engine, a gearbox, and an overall engine efficiency rating. The fan assembly can include a plurality of fan blades. The vane assembly can include a plurality of vanes, and the vanes can, in some instances, be disposed aft of the fan blades. The core engine can include a low-pressure turbine. The gearbox includes an input and an output. The input of the gearbox is coupled to the low-pressure turbine of the core engine and comprises a first rotational speed, the output of the gearbox is coupled to the fan assembly and has a second rotational speed, and a gear ratio of the first rotational speed to the second rotational speed is within a range of 3.2-4.0. The overall engine efficiency rating is within a range of 0.57-8.0.

Description

ACKNOWLEDGMENT OF GOVERNMENT SUPPORT[0001]The project leading to this application has received funding from the Clean Sky 2 Joint Undertaking (JU) under grant agreement No. 945541. The JU receives support from the European Union's Horizon 2020 research and innovation programme and the Clean Sky 2 JU members other than the Union.CROSS-REFERENCE TO RELATED APPLICATION[0002]This application claims the benefit of Italian Application No. 102022000001613, filed Jan. 31, 2022. The prior application is incorporated herein by reference in its entirety.FIELD[0003]This disclosure relates generally to turbomachines comprising a gearbox and particularly to geared turbofan engines.BACKGROUND[0004]A turbofan engine includes a core engine that drives a bypass fan. The bypass fan generates the majority of the thrust of the turbofan engine. The generated thrust can be used to move a payload (e.g., an aircraft).[0005]In some instances, a turbofan engine is configured as a direct drive engine. Direct d...

Claims

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Application Information

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IPC IPC(8): F02C7/36F02C3/067F02K3/06
CPCF02C7/36F02C3/067F02K3/06F05D2200/13F05D2200/14F05D2200/221F05D2260/40311F05D2260/98F02C3/04F05D2220/325F02K3/025F02C6/206Y02T50/60
Inventor PIAZZA, ANDREACLEMENTS, JEFFREY D.
Owner GE AVIO
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